
[Federal Register Volume 80, Number 214 (Thursday, November 5, 2015)]
[Rules and Regulations]
[Pages 68432-68434]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27919]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1425; Directorate Identifier 2014-NM-185-AD; 
Amendment 39-18312; AD 2015-22-07]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 
188 series airplanes. This AD was prompted by an evaluation by the 
design approval holder (DAH) indicating that the circumferential 
fuselage splice at fuselage-station (FS) 695 is subject to widespread 
fatigue damage (WFD). This AD requires an inspection for corrosion and 
previous repairs, severed stringers, cracking, and loose or distressed 
fasteners of the forward and aft ends of the stringer splices of 
certain stringers, inspection for cracking and modification of certain 
fastener holes common to the stringer and splice member at the forward 
and aft ends of the splice, and related investigative and corrective 
actions if necessary. We are issuing this AD to prevent loss of 
residual strength of the circumferential fuselage splice at FS 695, 
which could lead to rapid decompression of the cabin and potential loss 
of the airplane.

DATES: This AD is effective December 10, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 10, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, GA 30063; phone: 770-494-5444; fax: 770-494-5445; 
email: ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1425.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1425; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Carl Gray, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office 
(ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404-474-
5554; fax: 404-474-5605; email: carl.w.gray@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Model 188 series 
airplanes. The NPRM published in the Federal Register on May 28, 2015 
(80 FR 30391). The NPRM was prompted by an evaluation by the DAH 
indicating that a certain circumferential fuselage splice is subject to 
WFD. The NPRM proposed to require an inspection for corrosion and 
previous repairs, severed stringers, cracking, and loose or distressed 
fasteners of the forward and aft ends of the stringer splices of 
certain stringers, inspection for cracking and modification of certain 
fastener holes common to the stringer and splice member at the forward 
and aft ends of the splice, and related investigative and corrective 
actions if necessary. We are issuing this AD to prevent loss of 
residual strength of a certain circumferential fuselage splice, which 
could lead to rapid decompression of the cabin and potential loss of 
the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 30391, May 28, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 30391, May 28, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 30391, May 28, 2015).

Related Service Information Under 1 CFR Part 51

    We reviewed Lockheed Martin Electra Service Bulletin 88/SB-722, 
dated April 30, 2014. This service bulletin describes procedures for 
doing the following actions:
     A general visual inspection (GVI) for corrosion and 
previous repairs, severed stringers, cracking, and loose or distressed 
fasteners of the forward and aft ends of the stringer splices of 
stringers 1-7 and 66-72, and corrective actions if necessary.
     At stringers 1-7 and 66-72, removing the four rivets 
common to the stringer and splice member at the forward and aft ends of 
the splice and doing a bolt hole eddy current (BHEC) inspection or an 
equivalent inspection procedure for cracking in each of the fastener 
holes, and corrective actions if necessary.
     Corrective actions for cracked holes include reaming to 
the maximum permissible hole diameter of the next larger size rivet. If 
a crack indication remains after reaming, this service information 
specifies repairing the cracked stringer.
     If a severed stringer is found during the GVI, doing 
related investigative actions of an eddy current surface scan 
inspection for cracking of the fuselage skin at the skin-to-stringer 
attachments immediately forward and aft of the stringer break and 
confirming skin cracks with a dye penetrant inspection. Corrective 
actions include repairing the severed stringer or skin cracks.

[[Page 68433]]

     For holes without crack indications, other specified 
actions include modifying the fastener holes by reaming to a certain 
maximum permissible hole diameter of the same size rivet and installing 
replacement fasteners; or if the original hole is larger than the 
maximum permissible diameter, installing the next rivet size and type.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
AD.

Costs of Compliance

    We estimate that this AD affects 4 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspections and Modification........  18 work-hours x $85 per          $5,000           $6,530          $26,120
                                       hour = $1,530.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-22-07 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-18312 ; Docket No. FAA-2015-1425; Directorate 
Identifier 2014-NM-185-AD.

(a) Effective Date

    This AD is effective December 10, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Model 188A and 188C airplanes, certificated in 
any category, serial numbers 1001 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the circumferential fuselage splice at 
fuselage-station (FS) 695 is subject to widespread fatigue damage 
(WFD). We are issuing this AD to prevent loss of residual strength 
of the circumferential fuselage splice at FS 695, which could lead 
to rapid decompression of the cabin and potential loss of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspections, Modification, Related Investigative Actions, and 
Corrective Actions

    Before the accumulation of 38,200 total flight hours or within 
30 days after the effective date of this AD, whichever occurs later: 
Do a general visual inspection for corrosion and previous repairs, 
severed stringers, cracking, and loose or distressed fasteners of 
the forward and aft ends of the stringer splices of stringers 1-7 
and 66-72; remove the four rivets common to the stringer and splice 
member at the forward and aft ends of the splice and do a bolt hole 
eddy current inspection or an equivalent inspection procedure for 
cracking in each of the fastener holes; modify the fastener holes; 
and do all applicable related investigative and corrective actions 
and other specified actions; in accordance with the Accomplishment 
Instructions of Lockheed Martin Electra Service Bulletin 88/SB-722, 
dated April 30, 2014, except as specified in paragraph (h) of this 
AD. Do all applicable related investigative and corrective actions 
and other specified actions before further flight. If any repairs 
exceed the repair limits specified in Lockheed Martin Electra 
Service Bulletin 88/SB-722, dated April 30, 2014, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (j) of this AD.

(h) Corrective Action

    (1) If, during any inspection required by paragraph (g) of this 
AD, any corrosion or previous repair is found, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (j) of this AD.
    (2) If, during any inspection required by paragraph (g) of this 
AD, any loose or distressed fastener is found, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (j) of this AD.

(i) Exception

    Although Lockheed Martin Electra Service Bulletin 88/SB-722, 
dated April 30, 2014,

[[Page 68434]]

specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
ACO, send it to the attention of the person identified in paragraph 
(k) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

 (k) Related Information

    For more information about this AD, Carl Gray, Aerospace 
Engineer, Airframe Branch, ACE-117A, FAA, Atlanta ACO, 1701 Columbia 
Avenue, College Park, GA 30337; phone: 404-474-5554; fax: 404-474-
5605; email: carl.w.gray@faa.gov.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Lockheed Martin Electra Service Bulletin 88/SB-722, dated 
April 30, 2014.
    (ii) Reserved.
    (3) For Lockheed service information identified in this AD, 
contact Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 
86 S. Cobb Drive, Marietta, GA 30063; phone: 770-494-5444; fax: 770-
494-5445; email: ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27919 Filed 11-4-15; 8:45 am]
BILLING CODE 4910-13-P


